EPPLER 541 AIRFOIL (e541-il)
EPPLER 541 AIRFOIL - Eppler E541 general aviation airfoil
| Details | Dat file | Parser | |
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(e541-il) EPPLER 541 AIRFOIL Eppler E541 general aviation airfoil Max thickness 16.6% at 46.2% chord. Max camber 1.7% at 36.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 541 AIRFOIL
36. 37.
0.0000100 0.0002200
0.0000600 0.0008800
0.0003400 0.0022800
0.0008400 0.0037800
0.0019500 0.0061600
0.0026300 0.0073500
0.0101600 0.0161400
0.0223600 0.0255900
0.0390700 0.0352600
0.0601500 0.0448600
0.0853900 0.0541500
0.1145800 0.0629300
0.1474500 0.0710300
0.1836700 0.0783200
0.2229000 0.0846700
0.2647400 0.0899900
0.3087600 0.0941800
0.3545000 0.0971700
0.4014800 0.0989100
0.4491600 0.0993200
0.4970400 0.0983200
0.5445500 0.0957400
0.5913200 0.0913200
0.6372400 0.0848400
0.6825100 0.0764400
0.7270700 0.0668000
0.7704300 0.0566100
0.8120100 0.0463600
0.8511500 0.0365300
0.8871700 0.0275300
0.9193100 0.0196600
0.9468200 0.0131100
0.9689800 0.0078300
0.9854800 0.0036100
0.9961700 0.0008800
1.0000000 0.0000000
0.0000100 0.0002200
0.0000100 -.0004100
0.0001100 -.0009900
0.0003100 -.0015500
0.0006100 -.0021300
0.0009900 -.0027100
0.0019600 -.0039100
0.0032000 -.0051400
0.0055100 -.0070300
0.0148700 -.0126100
0.0308000 -.0192100
0.0518500 -.0256700
0.0777700 -.0318800
0.1082800 -.0377700
0.1430200 -.0433200
0.1815300 -.0485000
0.2233100 -.0532500
0.2678200 -.0574800
0.3145300 -.0610900
0.3628700 -.0639900
0.4122700 -.0660700
0.4621500 -.0672400
0.5119400 -.0673900
0.5610400 -.0663700
0.6088900 -.0640300
0.6548600 -.0599400
0.6990300 -.0533900
0.7421200 -.0443900
0.7847800 -.0338300
0.8268800 -.0233900
0.8672000 -.0143700
0.9043600 -.0073900
0.9370000 -.0027300
0.9638301 0.0002600
0.9837200 0.0004600
0.9959100 0.0002400
1.0000000 0.0000000
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Polars for EPPLER 541 AIRFOIL (e541-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e541-il | 50,000 | 9 | 25.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 50,000 | 5 | 21 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 100,000 | 9 | 40.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 100,000 | 5 | 29.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 200,000 | 9 | 46.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 200,000 | 5 | 50.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 500,000 | 9 | 78.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 500,000 | 5 | 79.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 1,000,000 | 9 | 106.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 1,000,000 | 5 | 96.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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